EP3303812A1 - Additive manufactured combustible element with fuel and oxidizer - Google Patents

Additive manufactured combustible element with fuel and oxidizer

Info

Publication number
EP3303812A1
EP3303812A1 EP16708787.3A EP16708787A EP3303812A1 EP 3303812 A1 EP3303812 A1 EP 3303812A1 EP 16708787 A EP16708787 A EP 16708787A EP 3303812 A1 EP3303812 A1 EP 3303812A1
Authority
EP
European Patent Office
Prior art keywords
oxidizer
fuel
regions
combustible element
combustible
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP16708787.3A
Other languages
German (de)
French (fr)
Other versions
EP3303812B1 (en
Inventor
Jeremy C. DANFORTH
Mark T. LANGHENRY
Matt H. SUMMERS
Teresa E. PERDUE
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Co
Original Assignee
Raytheon Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Raytheon Co filed Critical Raytheon Co
Publication of EP3303812A1 publication Critical patent/EP3303812A1/en
Application granted granted Critical
Publication of EP3303812B1 publication Critical patent/EP3303812B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
    • C06B45/04—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
    • C06B45/06—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
    • C06B45/10—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
    • C06B21/0033—Shaping the mixture
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/12—Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition

Definitions

  • the invention is in the field of combustible elements, such as for rocket motors or other energetic components.
  • Additive-manufactured fuel grains have been produced before, albeit for rocket motors using conventional metal casings and nozzles.
  • a combustible element includes a matrix of fuel regions and oxidizer regions.
  • the element may be made by an additive manufacturing process, with the fuel and oxidizer regions laid down in a number of layers.
  • a combustible element includes fuel; and oxidizer; wherein the fuel and the oxidizer are interspersed in discrete separate regions within a single solid element; and wherein the combustible element defines a combustion chamber therewithin where combustion of the fuel and the oxidizer occurs upon ignition of the fuel and the oxidizer.
  • the regions include: fuel regions that contain the fuel; and oxidizer regions that contain the oxidizer; and the oxidizer regions also contain a continuous material that acts as a binder.
  • the separate regions make up a matrix of regularly-ordered fuel regions and oxidizer regions, with alternating fuel regions and oxidizer regions.
  • the element is produced by an additive manufacturing process.
  • the fuel includes a first thermoplastic continuous material, with a metal additive.
  • the oxidizer includes a second thermoplastic continuous material, with an oxidizer additive.
  • the oxidizer additive includes beads of oxidizer material within the second thermoplastic continuous material.
  • the oxidizer additive includes droplets of oxidizer material within the second
  • thermoplastic continuous material thermoplastic continuous material.
  • the fuel-to-oxidizer ratio varies within the solid element, thereby producing one or more of variations in burn rate, or variation of combustion temperature.
  • a method of producing a combustible element includes: successively depositing multiple layers of the element in an additive manufacturing process; wherein the depositing each of the layers includes depositing a matrix of discrete fuel regions that include a fuel material, and discrete oxidizer regions that include an oxidizer material, for that layer.
  • the depositing includes selectively depositing fuel material and oxidizer material from heads that are movable relative to the combustible element.
  • the heads include heads for extruding the fuel material and the oxidizer material.
  • the fuel material and the oxidizer material extruded by the heads is heated material.
  • the fuel material and the oxidizer material both include thermoplastic continuous material, used as an extrudable base for the materials.
  • the fuel material includes a fuel additive; and the oxidizer material includes an oxidizer additive.
  • the method is part of production of a larger structure that the combustible element is a portion of, with portions of the larger structure that are adjacent to the combustible element are also made by an additive manufacturing process.
  • the depositing includes depositing different relative amounts of the fuel and the oxidizer in different of the layers.
  • the depositing different relative amounts includes varying the ratio of the fuel regions to the oxidizer regions.
  • the depositing different relative amounts includes varying size of the fuel regions and/or the oxidizer regions.
  • the depositing the layers includes leaving one or more cavities within the combustible element, wherein the one or more cavities are free of deposited material.
  • FIG. 1 is an oblique view of a combustible embodiment in accordance with an embodiment of the present invention.
  • Fig. 2 is a plan view of the combustible element of Fig. 1 .
  • Fig. 3 is a schematic view illustrating additive manufacture of the combustible element of Fig. 1.
  • Fig. 4 is an oblique view showing the combustible element of Fig. 1 as part of a structural part.
  • Fig. 5 is an oblique view of a first flying vehicle that includes combustible elements, in accordance with an embodiment of the invention.
  • Fig. 6 is an oblique view of a second flying vehicle that includes
  • a combustible element includes regions of fuel material interspersed with regions of oxidizer material.
  • the element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element.
  • the combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited.
  • An igniter may be positioned within or along the combustible element in order to initiate combustion.
  • the fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate.
  • the composition and/or amounts of the fuel and oxidizer regions may be varied at different locations within the combustible element, in order to produce desired burn characteristics at different times during the burning, or at different locations in the combustible element.
  • the combustible element may be a thrust-producing device, such as a rocket motor.
  • the rocket motor may be a nozzleless rocket motor, with the combustion chamber configured such that the pressurized gasses produced by the combustion become supersonic as they pass along the combustion chamber.
  • the combustible element may be an energetic device used for other purposes, for example to generate pressurized gasses for filling an air bag or other structure.
  • Figs. 1 and 2 show a combustible element 10 that is made up of a matrix of fuel regions 12 and oxidizer regions 14.
  • the fuel regions 12 and the oxidizer regions 14 are interspersed throughout the combustible element 10, although the relative frequency of the different types of regions may vary with position within the combustible element 10.
  • the fuel region 12 and the oxidizer regions 14 have a size that is larger than the size of individual particles of fuel and oxidizer materials.
  • the fuel regions 12 and the oxidizer regions 14 may have sizes that are on the order of 0.1 mm in extent.
  • the size of the particles may be from 50 to 600 pm (microns) in extent, for example, such as including coarse particles (about 400 to 600 pm) and/or medium particles (50 to 200 pm).
  • the oxidizer regions 14 may have multi-modal blends of multiple-sized particles in distributions to maximize the weight of oxidizer per unit volume. There may be relatively large particles that make up the bulk of the oxidizer volume, and relatively small particles with sizes selected to fill in part of the gaps between the larger particles. This increases the total potential propellant mass fraction of the element 10. Blends of different sized particles are also possible for the fuel regions 12 as well.
  • the fuel regions 12 may include a suitable fuel material, perhaps in conjunction with other suitable materials in order to make the fuel material suitable for use as a filament for extrusion in an additive manufacturing process.
  • a suitable fuel material is a thermoplastic continuous material doped with a metal.
  • the thermoplastic material may be a suitable material such as polylactide (PLA), acrylonitrile butadiene styrene (ABS), or a polyamide.
  • the added metal may be an energetic metal such as magnesium, aluminum, or zirconium.
  • the thermoplastic continuous material may be used itself as a fuel, without any sort of additive.
  • the fuel may be added into the thermoplastic binder in powder form.
  • the fuel powder may be mixed into the thermoplastic material during the manufacturing process of the filament itself.
  • the powder may be controlled or characterized by typical key characteristics which include, but are not limited to, chemical reaction characteristics, grade/purity, and particle size.
  • the oxidizer regions 14 may also include a suitable thermoplastic material as a continuous material, such as those described in the previous paragraphs, in combination with an added oxidizer.
  • the added oxidizer may include small droplets or beads of oxidizer material that are within the thermoplastic material. For example there may be three sizes of particles/droplets, with the two smaller sizes of particles/droplets able to be located in the spaces between adjacent large particles.
  • Powdered oxidizer material may also be added to a thermoplastic binder material, such as during the manufacturing process of the filament used to produce the oxidizer regions 14. Characteristics taken into consideration may include chemical reactiveness, grade/purity, and particle size.
  • the added oxidizer may be a material such as strontium perchlorate, other perchlorate oxidizers (e.g., ammonium or potassium), nitrate oxidizers (e.g., ammonium or potassium), or ammonium dinitramine, to give a few possibilities.
  • burn rate additives e.g., n-Butyl ferrocene, oxides of copper, lead, zirconium, or iron, and other conventional burn rate additives
  • combustion stability additives any of a variety of suitable metals, such as magnesium or zirconium
  • additives to make a translucent or other light-transmitting material opaque solid explosive fillers, such as HMX or RDX, and processing aids that may be required to obtain desirable viscosities, stabilities, etc. that make the filaments more amenable to the fused deposition process.
  • the regions 12 and 14 may be placed in an ordered configuration in which the regions 12 and 14 are deliberately placed during manufacture of the combustible element 10.
  • the combustible element 10 may be produced using an additive manufacturing technique, using separate print heads 20 and 22, used to deposit the regions 12 and 14, respectively.
  • the heads 20 and 22 may be computer controlled to place the regions 12 and 14 in desired locations within the element 10.
  • the element 10 may be built up layer by layer, for example, with the heads 20 and 22 moving and dispensing material, such as filaments of fuel and oxidizer material) to provide the desired regions 12 and 14 in the desired locations within each layer.
  • the movement of the heads 20 and 22, and the dispensing of the fuel and oxidizer material from the heads 20 and 22, may be controlled by a computer or other suitable controller.
  • the heads 20 and 22 may move together, with suitable fuel or oxidizer material dispensed at suitable locations and in suitable amounts at selected locations.
  • the fuel and oxidizer materials (for example suitable filaments of the materials) may be heated and extruded at the desired locations, as part of a fused deposition additive manufacturing process.
  • Suitable machines for performing this function include any of a variety two- extruder fused deposition modeling (FDM) machines, or more broadly all suitable FDM machines with at least two extruders such that the deposited quantity of fuel and oxidizer filaments can vary independently.
  • the nozzle extruder deposition diameter for such machines may be at least approximately twice the maximum fuel particle size distributed within the filament.
  • Machines for performing other sorts of additive manufacturing processes are alternatives to the use of FDM machines.
  • the regions 12 and 14 may be any of a variety of variations in the regions 12 and 14 throughout the element 10.
  • the relative amounts of fuel and oxidizer may be varied at different locations within the element 10 by varying the size, composition, and/or placement of the regions 12 and 14. For example, at different longitudinal (axial) and/or radial locations within the element, there may be different ratios of fuel regions 12 to oxidizer regions 14, to provide different combustion characteristics when burning different parts of the element 10.
  • Varying or controlling the fuel-oxidizer mixture ratio may involve varying the fuel geometry, or the fuel material or blend of materials that make up the fuel. This could be done to raise or lower the flame temperature of the combustion. High flame temperatures go along with high combustion efficiency and high thrust performance. Low flame temperatures result in lower combustion efficiency, but cooler output for gas generator or non-thrust uses. For example, a relatively low flame temperature may be required for a gas generator that is used as a start cartridge to start a turbine engine, such as for a missile such as a cruise missile. In such a situation it is desirable to generate a large gas volume flow rate, without the gas having a high temperature that might stress components of the turbine engine. In contrast, a thrust-producing fuel element could have a greater amount of oxidizer, which would result in high temperature combustion with increased efficiency.
  • the additive manufacture of the element 10 may also include leaving open spaces or chambers 28 within the element 10, to serve as combustion chambers, or for other purposes.
  • the chamber 28 may be configured as a combustion chamber in which the combustion products (pressurized gases) transition to supersonic flow within the chamber, enabling use of the element 10 as a rocket motor.
  • Other purposes for the spaces or chambers 28 may include embedding additional components, such as igniters, in the element.
  • the element 10 has a cylindrical shape, and the chamber 28 is a central opening in the element 10.
  • the element 10 may have any of a wide variety of regular or irregular other shapes, and/or there may be chambers or open spaces of any of a variety of shapes, suitable for use as combustion chambers, or for other purposes.
  • the element 10 may be part of a larger structure 100, which also may be formed in an additive manufacturing process.
  • Material 102 of the structure 100 may surround the element 10.
  • the material 102 may be continuous with the material of the element 10, and may be made of a similar type of material, and/or may be manufactured using a similar process.
  • the material 102 may be based on a thermoplastic material, for example the same thermoplastic material used as a continuous material for the fuel regions 12 and/or the oxidizer regions 14 (Fig. 1 ).
  • thermoplastic or other material of the larger structure 100 may also function to some extent as a fuel, since it may be combustible.
  • the element 10 may be configured to avoid or limit combustion of the material 102, for instance by limiting the amount of oxidizer in the element 10. This may allow the structure 100 to avoid undue weakening from the combustion of the element 10.
  • the larger structure 100 may be part of a fuselage or other portion of a flying vehicle, such as a space vehicle 150 (Fig. 5) or an air vehicle 200 (Fig. 6).
  • the elements 10 may be placed at suitable locations around the vehicles 150 and 200, to serve as rocket motors or other thrust- producing elements.
  • Elements 10 may be located in a fuselage 152 of the space vehicle 150, or in a fuselage 202, wings 204, canards 206, elevators 208, and/or a rudder 210 of the air vehicle.
  • the elements 10 may be selectively fired for steering, changing orientation, course correction, or other purposes.
  • the element 10 may be an insert that is formed separately and placed within a suitable opening in the structure 100.
  • the element 10 may be placed within a casing, such a metal casing, prior to be inserted into the opening in the structure 100.
  • the combustible element and the associated structures provide many benefits.
  • the composition of the element can be controlled and tailored to achieve specific desired burn characteristics. Chambers within the element can be constructed during formation of the element, with a wide range of geometry of the chambers achievable.
  • the element may be easily integrated with a wide variety of different structural parts, such as parts of flying vehicles.
  • the elements of flying vehicles such as parts of flying vehicles.
  • combustible element may be used for other purposes, such as for production of pressurized gases to fill an air bag or other structure.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Dispersion Chemistry (AREA)
  • Molecular Biology (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Air Bags (AREA)

Abstract

A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element. The combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited. The fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate.

Description

ADDITIVE MANUFACTURED COMBUSTIBLE
ELEMENT WITH FUEL AND OXIDIZER
FIELD OF THE INVENTION
[0001] The invention is in the field of combustible elements, such as for rocket motors or other energetic components.
DESCRIPTION OF THE RELATED ART
[0002] Additive-manufactured fuel grains have been produced before, albeit for rocket motors using conventional metal casings and nozzles.
SUMMARY OF THE INVENTION
[0003] A combustible element includes a matrix of fuel regions and oxidizer regions. The element may be made by an additive manufacturing process, with the fuel and oxidizer regions laid down in a number of layers.
[0004] According to an aspect of the invention, a combustible element includes fuel; and oxidizer; wherein the fuel and the oxidizer are interspersed in discrete separate regions within a single solid element; and wherein the combustible element defines a combustion chamber therewithin where combustion of the fuel and the oxidizer occurs upon ignition of the fuel and the oxidizer.
[0005] According to an embodiment of the device of any prior paragraph(s), the regions include: fuel regions that contain the fuel; and oxidizer regions that contain the oxidizer; and the oxidizer regions also contain a continuous material that acts as a binder.
[0006] According to an embodiment of the device of any prior paragraph(s), the separate regions make up a matrix of regularly-ordered fuel regions and oxidizer regions, with alternating fuel regions and oxidizer regions.
[0007] According to an embodiment of the device of any prior paragraph(s), the element is produced by an additive manufacturing process.
[0008] According to an embodiment of the device of any prior paragraph(s), the fuel includes a first thermoplastic continuous material, with a metal additive. [0009] According to an embodiment of the device of any prior paragraph(s), the oxidizer includes a second thermoplastic continuous material, with an oxidizer additive.
[0010] According to an embodiment of the device of any prior paragraph(s), the oxidizer additive includes beads of oxidizer material within the second thermoplastic continuous material.
[0011] According to an embodiment of the device of any prior paragraph(s), the oxidizer additive includes droplets of oxidizer material within the second
thermoplastic continuous material.
[0012] According to an embodiment of the device of any prior paragraph(s), the fuel-to-oxidizer ratio varies within the solid element, thereby producing one or more of variations in burn rate, or variation of combustion temperature.
[0013] According to another aspect of the invention, a method of producing a combustible element includes: successively depositing multiple layers of the element in an additive manufacturing process; wherein the depositing each of the layers includes depositing a matrix of discrete fuel regions that include a fuel material, and discrete oxidizer regions that include an oxidizer material, for that layer.
[0014] According to an embodiment of the device of any prior paragraph(s), the depositing includes selectively depositing fuel material and oxidizer material from heads that are movable relative to the combustible element.
[0015] According to an embodiment of the device of any prior paragraph(s), the heads include heads for extruding the fuel material and the oxidizer material.
[0016] According to an embodiment of the device of any prior paragraph(s), the fuel material and the oxidizer material extruded by the heads is heated material.
[0017] According to an embodiment of the device of any prior paragraph(s), the fuel material and the oxidizer material both include thermoplastic continuous material, used as an extrudable base for the materials.
[0018] According to an embodiment of the device of any prior paragraph(s), the fuel material includes a fuel additive; and the oxidizer material includes an oxidizer additive.
[0019] According to an embodiment of the device of any prior paragraph(s), the method is part of production of a larger structure that the combustible element is a portion of, with portions of the larger structure that are adjacent to the combustible element are also made by an additive manufacturing process.
[0020] According to an embodiment of the device of any prior paragraph(s), the depositing includes depositing different relative amounts of the fuel and the oxidizer in different of the layers.
[0021] According to an embodiment of the device of any prior paragraph(s), the depositing different relative amounts includes varying the ratio of the fuel regions to the oxidizer regions.
[0022] According to an embodiment of the device of any prior paragraph(s), the depositing different relative amounts includes varying size of the fuel regions and/or the oxidizer regions.
[0023] According to an embodiment of the device of any prior paragraph(s), the depositing the layers includes leaving one or more cavities within the combustible element, wherein the one or more cavities are free of deposited material.
[0024] To the accomplishment of the foregoing and related ends, the invention comprises the features hereinafter fully described and particularly pointed out in the claims. The following description and the annexed drawings set forth in detail certain illustrative embodiments of the invention. These embodiments are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the drawings.
BRIEF DESCRIPTION OF DRAWINGS
[0025] The annexed drawings, which are not necessarily to scale, show various aspects of the invention.
[0026] Fig. 1 is an oblique view of a combustible embodiment in accordance with an embodiment of the present invention.
[0027] Fig. 2 is a plan view of the combustible element of Fig. 1 .
[0028] Fig. 3 is a schematic view illustrating additive manufacture of the combustible element of Fig. 1.
[0029] Fig. 4 is an oblique view showing the combustible element of Fig. 1 as part of a structural part. [0030] Fig. 5 is an oblique view of a first flying vehicle that includes combustible elements, in accordance with an embodiment of the invention.
[0031] Fig. 6 is an oblique view of a second flying vehicle that includes
combustible elements, in accordance with an embodiment of the invention.
DETAILED DESCRIPTION
[0032] A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element. The combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited. An igniter may be positioned within or along the combustible element in order to initiate combustion. The fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate. The composition and/or amounts of the fuel and oxidizer regions may be varied at different locations within the combustible element, in order to produce desired burn characteristics at different times during the burning, or at different locations in the combustible element.
[0033] The combustible element may be a thrust-producing device, such as a rocket motor. The rocket motor may be a nozzleless rocket motor, with the combustion chamber configured such that the pressurized gasses produced by the combustion become supersonic as they pass along the combustion chamber.
Alternatively, the combustible element may be an energetic device used for other purposes, for example to generate pressurized gasses for filling an air bag or other structure.
[0034] Figs. 1 and 2 show a combustible element 10 that is made up of a matrix of fuel regions 12 and oxidizer regions 14. The fuel regions 12 and the oxidizer regions 14 are interspersed throughout the combustible element 10, although the relative frequency of the different types of regions may vary with position within the combustible element 10. For example, there may be a matrix of alternating fuel regions 12 and oxidizer regions 14 within a layer. The fuel region 12 and the oxidizer regions 14 have a size that is larger than the size of individual particles of fuel and oxidizer materials. For example, the fuel regions 12 and the oxidizer regions 14 may have sizes that are on the order of 0.1 mm in extent. The size of the particles may be from 50 to 600 pm (microns) in extent, for example, such as including coarse particles (about 400 to 600 pm) and/or medium particles (50 to 200 pm).
[0035] More than one size of particles may be used. For example the oxidizer regions 14 may have multi-modal blends of multiple-sized particles in distributions to maximize the weight of oxidizer per unit volume. There may be relatively large particles that make up the bulk of the oxidizer volume, and relatively small particles with sizes selected to fill in part of the gaps between the larger particles. This increases the total potential propellant mass fraction of the element 10. Blends of different sized particles are also possible for the fuel regions 12 as well.
[0036] The fuel regions 12 may include a suitable fuel material, perhaps in conjunction with other suitable materials in order to make the fuel material suitable for use as a filament for extrusion in an additive manufacturing process. An example of a suitable fuel material is a thermoplastic continuous material doped with a metal. The thermoplastic material may be a suitable material such as polylactide (PLA), acrylonitrile butadiene styrene (ABS), or a polyamide. The added metal may be an energetic metal such as magnesium, aluminum, or zirconium. As an alternative, the thermoplastic continuous material may be used itself as a fuel, without any sort of additive.
[0037] The fuel may be added into the thermoplastic binder in powder form. The fuel powder may be mixed into the thermoplastic material during the manufacturing process of the filament itself. The powder may be controlled or characterized by typical key characteristics which include, but are not limited to, chemical reaction characteristics, grade/purity, and particle size.
[0038] The oxidizer regions 14 may also include a suitable thermoplastic material as a continuous material, such as those described in the previous paragraphs, in combination with an added oxidizer. The added oxidizer may include small droplets or beads of oxidizer material that are within the thermoplastic material. For example there may be three sizes of particles/droplets, with the two smaller sizes of particles/droplets able to be located in the spaces between adjacent large particles. Powdered oxidizer material may also be added to a thermoplastic binder material, such as during the manufacturing process of the filament used to produce the oxidizer regions 14. Characteristics taken into consideration may include chemical reactiveness, grade/purity, and particle size.
[0039] Alternatively, the added oxidizer may be a material such as strontium perchlorate, other perchlorate oxidizers (e.g., ammonium or potassium), nitrate oxidizers (e.g., ammonium or potassium), or ammonium dinitramine, to give a few possibilities.
[0040] Other materials may be used as alternatives or in addition to those discussed above. Examples include burn rate additives (e.g., n-Butyl ferrocene, oxides of copper, lead, zirconium, or iron, and other conventional burn rate additives), combustion stability additives (any of a variety of suitable metals, such as magnesium or zirconium), additives to make a translucent or other light-transmitting material opaque, solid explosive fillers, such as HMX or RDX, and processing aids that may be required to obtain desirable viscosities, stabilities, etc. that make the filaments more amenable to the fused deposition process.
[0041] The regions 12 and 14 may be placed in an ordered configuration in which the regions 12 and 14 are deliberately placed during manufacture of the combustible element 10. With reference now in addition to Fig. 3, the combustible element 10 may be produced using an additive manufacturing technique, using separate print heads 20 and 22, used to deposit the regions 12 and 14, respectively. The heads 20 and 22 may be computer controlled to place the regions 12 and 14 in desired locations within the element 10. The element 10 may be built up layer by layer, for example, with the heads 20 and 22 moving and dispensing material, such as filaments of fuel and oxidizer material) to provide the desired regions 12 and 14 in the desired locations within each layer. The movement of the heads 20 and 22, and the dispensing of the fuel and oxidizer material from the heads 20 and 22, may be controlled by a computer or other suitable controller. The heads 20 and 22 may move together, with suitable fuel or oxidizer material dispensed at suitable locations and in suitable amounts at selected locations. The fuel and oxidizer materials (for example suitable filaments of the materials) may be heated and extruded at the desired locations, as part of a fused deposition additive manufacturing process.
[0042] Suitable machines for performing this function include any of a variety two- extruder fused deposition modeling (FDM) machines, or more broadly all suitable FDM machines with at least two extruders such that the deposited quantity of fuel and oxidizer filaments can vary independently. The nozzle extruder deposition diameter for such machines may be at least approximately twice the maximum fuel particle size distributed within the filament. Machines for performing other sorts of additive manufacturing processes are alternatives to the use of FDM machines.
[0043] There may be any of a variety of variations in the regions 12 and 14 throughout the element 10. The relative amounts of fuel and oxidizer may be varied at different locations within the element 10 by varying the size, composition, and/or placement of the regions 12 and 14. For example, at different longitudinal (axial) and/or radial locations within the element, there may be different ratios of fuel regions 12 to oxidizer regions 14, to provide different combustion characteristics when burning different parts of the element 10.
[0044] Varying or controlling the fuel-oxidizer mixture ratio may involve varying the fuel geometry, or the fuel material or blend of materials that make up the fuel. This could be done to raise or lower the flame temperature of the combustion. High flame temperatures go along with high combustion efficiency and high thrust performance. Low flame temperatures result in lower combustion efficiency, but cooler output for gas generator or non-thrust uses. For example, a relatively low flame temperature may be required for a gas generator that is used as a start cartridge to start a turbine engine, such as for a missile such as a cruise missile. In such a situation it is desirable to generate a large gas volume flow rate, without the gas having a high temperature that might stress components of the turbine engine. In contrast, a thrust-producing fuel element could have a greater amount of oxidizer, which would result in high temperature combustion with increased efficiency.
[0045] The additive manufacture of the element 10 may also include leaving open spaces or chambers 28 within the element 10, to serve as combustion chambers, or for other purposes. The chamber 28 may be configured as a combustion chamber in which the combustion products (pressurized gases) transition to supersonic flow within the chamber, enabling use of the element 10 as a rocket motor. Other purposes for the spaces or chambers 28 may include embedding additional components, such as igniters, in the element.
[0046] In the illustrated embodiment the element 10 has a cylindrical shape, and the chamber 28 is a central opening in the element 10. Alternatively the element 10 may have any of a wide variety of regular or irregular other shapes, and/or there may be chambers or open spaces of any of a variety of shapes, suitable for use as combustion chambers, or for other purposes.
[0047] Referring now to Fig. 4, the element 10 may be part of a larger structure 100, which also may be formed in an additive manufacturing process. Material 102 of the structure 100 may surround the element 10. The material 102 may be continuous with the material of the element 10, and may be made of a similar type of material, and/or may be manufactured using a similar process. For example, the material 102 may be based on a thermoplastic material, for example the same thermoplastic material used as a continuous material for the fuel regions 12 and/or the oxidizer regions 14 (Fig. 1 ).
[0048] The thermoplastic or other material of the larger structure 100 may also function to some extent as a fuel, since it may be combustible. However the element 10 may be configured to avoid or limit combustion of the material 102, for instance by limiting the amount of oxidizer in the element 10. This may allow the structure 100 to avoid undue weakening from the combustion of the element 10.
[0049] The larger structure 100 may be part of a fuselage or other portion of a flying vehicle, such as a space vehicle 150 (Fig. 5) or an air vehicle 200 (Fig. 6). As seen with reference to those two figures, the elements 10 may be placed at suitable locations around the vehicles 150 and 200, to serve as rocket motors or other thrust- producing elements. Elements 10 may be located in a fuselage 152 of the space vehicle 150, or in a fuselage 202, wings 204, canards 206, elevators 208, and/or a rudder 210 of the air vehicle. The elements 10 may be selectively fired for steering, changing orientation, course correction, or other purposes.
[0050] As an alternative to be a unitary part of a larger structure 100, the element 10 may be an insert that is formed separately and placed within a suitable opening in the structure 100. The element 10 may be placed within a casing, such a metal casing, prior to be inserted into the opening in the structure 100. [0051] The combustible element and the associated structures provide many benefits. The composition of the element can be controlled and tailored to achieve specific desired burn characteristics. Chambers within the element can be constructed during formation of the element, with a wide range of geometry of the chambers achievable. The element may be easily integrated with a wide variety of different structural parts, such as parts of flying vehicles. In addition, the
combustible element may be used for other purposes, such as for production of pressurized gases to fill an air bag or other structure.
[0052] Although the invention has been shown and described with respect to a certain preferred embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. In particular regard to the various functions performed by the above described elements
(components, assemblies, devices, compositions, etc.), the terms (including a reference to a "means") used to describe such elements are intended to correspond, unless otherwise indicated, to any element which performs the specified function of the described element (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments of the invention. In addition, while a particular feature of the invention may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.

Claims

CLAIMS What is claimed is:
1 . A combustible element comprises:
fuel; and
oxidizer;
wherein the fuel and the oxidizer are interspersed in discrete separate regions within a single solid element; and
wherein the combustible element defines a combustion chamber therewithin where combustion of the fuel and the oxidizer occurs upon ignition of the fuel and the oxidizer.
2. The combustible element of claim 1 ,
wherein the regions include:
fuel regions that contain the fuel; and
oxidizer regions that contain the oxidizer; and
wherein the oxidizer regions also contain a continuous material that acts as a binder.
3. The combustible element of claim 1 or claim 2, wherein the separate regions make up a matrix of regularly-ordered fuel regions and oxidizer regions, with alternating fuel regions and oxidizer regions.
4. The combustible element of any of claims 1 to 3, wherein the element is produced by an additive manufacturing process.
5. The combustible element of any of claims 1 to 4, wherein the fuel includes a first thermoplastic continuous material, with a metal additive.
6. The combustible element of any of claims 1 to 5, wherein the oxidizer includes a second thermoplastic continuous material, with an oxidizer additive.
7. The combustible element of claim 6, wherein the oxidizer additive includes beads of oxidizer material within the second thermoplastic continuous material.
8. The combustible element of claim 6, wherein the oxidizer additive includes droplets of oxidizer material within the second thermoplastic continuous material.
9. The combustible element of any of claims 1 to 8, wherein the fuel-to- oxidizer ratio varies within the solid element, thereby producing one or more of variations in burn rate, or variation of combustion temperature.
10. A method of producing a combustible element, the method comprising: successively depositing multiple layers of the element in an additive manufacturing process;
wherein the depositing each of the layers includes depositing a matrix of discrete fuel regions that include a fuel material, and discrete oxidizer regions that include an oxidizer material, for that layer.
1 1 . The method of claim 10, wherein the depositing includes selectively depositing fuel material and oxidizer material from heads that are movable relative to the combustible element.
12. The method of claim 1 1 , wherein the heads include heads for extruding the fuel material and the oxidizer material.
13. The method of claim 12, wherein the fuel material and the oxidizer material extruded by the heads is heated material.
14. The method of claim 12 or claim 13, wherein the fuel material and the oxidizer material both include thermoplastic continuous material, used as an extrudable base for the materials.
15. The method of claim 14,
wherein the fuel material includes a fuel additive; and
wherein the oxidizer material includes an oxidizer additive.
16. The method of any of claims 10 to 15, wherein the method is part of production of a larger structure that the combustible element is a portion of, with portions of the larger structure that are adjacent to the combustible element are also made by an additive manufacturing process.
17. The method of any of claims 10 to 16, wherein the depositing includes depositing different relative amounts of the fuel and the oxidizer in different of the layers.
18. The method of claim 17, wherein the depositing different relative amounts includes varying the ratio of the fuel regions to the oxidizer regions.
19. The method of claim 17 or claim 18, wherein the depositing different relative amounts includes varying size of the fuel regions and/or the oxidizer regions.
20. The method of any of claims 10 to 19, wherein the depositing the layers includes leaving one or more cavities within the combustible element, wherein the one or more cavities are free of deposited material.
EP16708787.3A 2015-06-03 2016-02-01 Additive manufactured combustible element with fuel and oxidizer Active EP3303812B1 (en)

Applications Claiming Priority (2)

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US14/729,429 US10093592B2 (en) 2015-06-03 2015-06-03 Additive manufactured combustible element with fuel and oxidizer
PCT/US2016/015960 WO2016195762A1 (en) 2015-06-03 2016-02-01 Additive manufactured combustible element with fuel and oxidizer

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USRE49765E1 (en) * 2007-03-22 2023-12-26 Firehawk Aerospace, Inc. Additive manufactured thermoplastic-nanocomposite aluminum hybrid rocket fuel grain and method of manufacturing same
US10093592B2 (en) 2015-06-03 2018-10-09 Raytheon Company Additive manufactured combustible element with fuel and oxidizer
US11027482B2 (en) * 2016-02-09 2021-06-08 Lawrence Livermore National Security, Llc Additive manufacturing of multi-component parts for customizable energetic systems
DE102019007092A1 (en) * 2019-10-11 2021-04-15 Mbda Deutschland Gmbh 3D printing process and 3D printing device
US12116957B1 (en) * 2020-05-20 2024-10-15 X-Bow Launch Systems Inc. 3D-printed rocket fuel grains, rocket engines and an additive manufacturing process
WO2023107497A2 (en) * 2021-12-07 2023-06-15 Firehawk Aerospace, Inc. Hybrid rocket engine fuel grains with compositional variations
CN114311656B (en) * 2021-12-31 2023-04-28 西安交通大学 Method for preparing composite solid propellant based on 3D printing special-shaped high-combustion-speed die

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US10654762B2 (en) 2020-05-19
US10093592B2 (en) 2018-10-09
WO2016195762A1 (en) 2016-12-08
US20190002362A1 (en) 2019-01-03
EP3303812B1 (en) 2020-07-08

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